Physics
Scientific paper
Jun 1983
adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1983jgcd....6..220g&link_type=abstract
Journal of Guidance, Control, and Dynamics (ISSN 0731-5090), vol. 6, May-June 1983, p. 220-222.
Physics
2
Geosynchronous Orbits, Satellite Perturbation, Spacecraft Control, Stationkeeping, Time Optimal Control, Trajectory Optimization, Gravitational Effects, Optimization, Spacecraft Maneuvers
Scientific paper
A control strategy for geosynchronous satellites is developed which produces a trajectory history with the maximum time between maneuvers and the minimum annual velocity change, leading to the optimum annual delta-V requirements. The solar-lunar gravitational perturbations which give rise to the need for plane change maneuvers are first reviewed. The control strategy permits the inclination trajectory to have a magnitude less than or equal to the minimum measurable inclination somewhere near the middle of its path. It thus has the greatest arc length through the constraint circle. This technique also determines the minimum annual velocity change required.
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